def setUp(self):
"""
This will setup a main wing with some default parameters. The remaining tests will calculate
the area and other related properties in numerous ways.
The two equations are:
S = f(Lift_LO, V_Stall)
S = f(AR, b)
If S is specified, on variable from each of the two equations must be specified.
If S is not specified, three other variables must be specified.
"""
Wing = self.Wing = ACMainWing(1)
Wing.Airfoil = ('../../Airfoils/S1223/S1223.dat',
'../../Airfoils/S1223')
Wing.TR = [1, 0.7, 0.7]
Wing.Fb = [0.3, 0.8, 1]
Wing.Gam = [0.0 * ARCDEG, 0.0 * ARCDEG, 0.0 * ARCDEG]
Wing.CEdge = 'LE'
Wing.ConstUpper = True
Wing.FullWing = True
Wing.Alt_LO = 600 * FT
#
# Setup consistent numbers for area calculations
#
self.Lift_LO = 27.00654 * LBF
self.V_Stall = 41.2699923511 * FT / SEC
self.AR = 16
self.b = 10 * FT
self.S = 900. * IN**2
# link path to Aerothon
sys.path.append(trunkDir)
# import Aerothon modules
from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM
from scalar.units import AsUnit
from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood,\
Balsa, Ultracote, Poplar
from Aerothon.ACWing import ACMainWing
from Aerothon.ACWingWeight import ACSolidWing, ACRibWing
#==============================================================================#
# WING MODEL
#==============================================================================#
# Create the wing
Wing = ACMainWing(1)
Wing.Airfoil = 'S1223_TC'
# lift-off conditions
Wing.Lift_LO = 55 * LBF # 151107: shiggins guess
#Wing.V_Stall = 38 * FT/SEC #SPH: where does this come from?
Wing.Alt_LO = 710 * FT # approximation for elevation in Ft. Worth, TX
# wing geometry (to launch 54.5 pounds under 200 feet)
#Wing.b = 188*IN # wing span
#Wing.S = 22*FT**2 # wing surface area
# More realistic 12 ft wing
Wing.b = 144 * IN # wing span
Wing.S = 18 * FT**2 # wing surface area
Wing.FullWing = True
from __future__ import division # let 5/2 = 2.5 rather than 2 from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM from scalar.units import AsUnit from Aerothon.ACWing import ACMainWing from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood, Balsa, Ultracote, AluminumTube, Aluminum from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.b = 144 *IN #Wing.V_Stall = 32.5* FT/SEC Wing.S = 3024*IN**2 Wing.Lift_LO = 60*LBF Wing.Alt_LO = 721 * FT Wing.V_LOstall = 1.1 ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 6*FT #Wing.LowerWing.b = 6*FT #=============================================================================== #b=150,S=3200
from __future__ import division # let 5/2 = 2.5 rather than 2 from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG from scalar.units import AsUnit from Aerothon.ACWing import ACMainWing from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood, Balsa from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.Lift_LO = 35 * LBF Wing.V_max_climb = 65 * FT / SEC Wing.V_Stall = 35 * FT / SEC Wing.Alt_LO = 920 * FT #Wing.AR = 5.0 Wing.b = 95 * IN ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 4.5*FT #Wing.LowerWing.b = 4*FT Wing.TR = [1, 0.85, 1] Wing.Gam = [0 * ARCDEG, 0 * ARCDEG, 0 * ARCDEG]
from __future__ import division # let 5/2 = 2.5 rather than 2 from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM from scalar.units import AsUnit from Aerothon.ACWing import ACMainWing from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood, Balsa, Ultracote from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.Lift_LO = None Wing.b = 148 * IN Wing.V_Stall = 38 * FT / SEC Wing.S = 3485 * IN**2 #Wing.Lift_LO = 55*LBF Wing.Alt_LO = 1150 * FT #Look what it typically is in marietta during the competition ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 4.5*FT #Wing.LowerWing.b = 4*FT #=============================================================================== #b=150,S=3200
# link path to Aerothon
#sys.path.append(trunkDir)
# import Aerothon modules
from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM
from scalar.units import AsUnit
from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood,\
Balsa, Ultracote, Poplar, AluminumBalsa
from Aerothon.ACWing import ACMainWing
from Aerothon.ACWingWeight import ACSolidWing, ACRibWing
#==============================================================================#
# WING MODEL
#==============================================================================#
# Create the wing
Wing = ACMainWing(1)
Wing.Airfoil = 'S1223_TC' # will probably stick with this airfoil because of past trade studies
# lift-off conditions
Wing.Lift_LO = 60 * LBF # aircraft max weight is 55lbs, will keep at 60lbs for safety factor
#Wing.V_Stall = 38 * FT/SEC #SPH: where does this come from?
Wing.Alt_LO = 197 * FT # approximation for elevation in Ft. Worth, TX
# wing geometry (to launch 54.5 pounds under 200 feet)
Wing.b = 143.5 * IN # wing span
Wing.S = 3300 * IN**2 # wing surface area using a constant chord length of 25in
Wing.FullWing = True
# Wing Chord vs Position
### Box Wing
from __future__ import division # let 5/2 = 2.5 rather than 2 from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG from scalar.units import AsUnit from Aerothon.ACWing import ACMainWing from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood, Balsa from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.Lift_LO = 60 * LBF # Desired lift at liftoff Wing.V_max_climb = 65 * FT / SEC # liftoff speed Wing.Alt_LO = 200 * FT # liftoff altitude Wing.AR = 8.0 # Aspect Ratio Wing.b = 12 * 12 * IN # Wingspan ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True Wing.Fb = [0.4, 0.8, 1] # Span fraction corresponding to inputs below Wing.TR = [1, 0.8, .7] # Taper ratio Wing.Gam = [20 * ARCDEG, 20 * ARCDEG, 20 * ARCDEG] # Dihedral Wing.Lam = [0 * ARCDEG, 0 * ARCDEG, 0 * ARCDEG] # wing sweep angles Wing.CEdge = 'LE' # Defines constant edge Wing.ConstUpper = True
# link path to Aerothon
#sys.path.append(trunkDir)
# import Aerothon modules
from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM
from scalar.units import AsUnit
from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood,\
Balsa, Ultracote, Poplar, AluminumBalsa
from Aerothon.ACWing import ACMainWing
from Aerothon.ACWingWeight import ACSolidWing, ACRibWing
#==============================================================================#
# WING MODEL
#==============================================================================#
# Create the wing
Wing = ACMainWing(1)
Wing.Airfoil = 'S1223'
# lift-off conditions
Wing.Lift_LO = 60 * LBF # Should this be 55 lbs or are you just playing it safe?
#Wing.V_Stall = 38 * FT/SEC #SPH: where does this come from?
Wing.Alt_LO = 197 * FT # approximation for elevation in Ft. Worth, TX
# wing geometry (to launch 54.5 pounds under 200 feet)
Wing.b = 144 * IN # wing span
Wing.S = 3744 * IN**2 # wing surface area (was 3695.04)
# More realistic 12 ft wing
#Wing.b = 144*IN # wing span
#Wing.S = 20*FT**2 # wing surface area
Wing.FullWing = True
from __future__ import division # let 5/2 = 2.5 rather than 2 from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM from scalar.units import AsUnit from Aerothon.ACWing import ACMainWing from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood, Balsa, Ultracote from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.Lift_LO = None Wing.b = 144 * IN Wing.V_Stall = 36 * FT / SEC Wing.S = 3117 * IN**2 #Wing.Lift_LO = 55*LBF Wing.Alt_LO = 1150 * FT #Look what it typically is in marietta during the competition Wing.V_LOstall = 1.2 #added by Brock Pleiman 10/7/13 ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 4.5*FT #Wing.LowerWing.b = 4*FT #===============================================================================
from __future__ import division # let 5/2 = 2.5 rather than 2 from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM from scalar.units import AsUnit from Aerothon.ACWing import ACMainWing from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood, Balsa, Ultracote from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.Lift_LO = None #Initially 147 inches, changed to 105 inches (0.6 total length) Wing.b = 105 * IN #96 #Initially 38 ft/sec Wing.V_Stall = 38 * FT / SEC #From Jake's Matlab calculation # Surface Area of wing Wing.S = 2147 * IN**2 #Wing.Lift_LO = 55*LBF #Was 2000 ft since last year's was in Texas Wing.Alt_LO = 200 * FT #Lakeland, FL's elevation ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 4.5*FT